US20120103685A1 - Aircraft cable routing harness - Google Patents
Aircraft cable routing harness Download PDFInfo
- Publication number
- US20120103685A1 US20120103685A1 US13/284,135 US201113284135A US2012103685A1 US 20120103685 A1 US20120103685 A1 US 20120103685A1 US 201113284135 A US201113284135 A US 201113284135A US 2012103685 A1 US2012103685 A1 US 2012103685A1
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- US
- United States
- Prior art keywords
- aircraft
- cable routing
- harness according
- routing harness
- aircraft cable
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G3/00—Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
- H02G3/02—Details
- H02G3/04—Protective tubing or conduits, e.g. cable ladders or cable troughs
- H02G3/0431—Wall trunking
Definitions
- the present invention relates to an aircraft cable routing harness. More specifically, the present invention relates to a cable routing harness having a conductor embedded therein, wherein the harness is a substantially inflexible structural member and may be used in a fuel quantity installation of an aircraft.
- cables are routed throughout aircraft and in particularly through aircraft wings using cable raceways.
- These raceways are generally constructed from aluminium and comprise channel sections into which cables can be secured. Such cables are often braided to provide electro-magnetic protection.
- the raceway serves to guide and secure the cables and protect them from external mechanical damage.
- the cables are often secured in place in the raceway channels using clips.
- Fuel quantity installation (FQI) cable harnesses are routed through aircraft fuel tanks, in particular through the tanks in aircraft wings. These harnesses are clipped to the aircraft structure to hold them in place. Such harnesses are often braided or routed in a multi-layered conduit to provide electro-magnetic protection. Such structures also provide multiple layer protection to ensure that the wires are not exposed, even if the outer layers are damaged.
- raceways add significant weight to the aircraft.
- the cables are relatively free to move within the raceways which may affect their proximity (i.e. potentially causing problems with electro-magnetic interference) and may cause friction between adjacent cables. This is undesirable.
- known harnesses are relatively flexible and therefore must be clipped quite frequently along their length. This adds weight to the aircraft and makes the assembly process lengthy and costly.
- a further technical challenge in this field is to manage interference from adjacent conductors, and to prevent build up of static charge which could otherwise cause arcing.
- an aircraft cable routing harness comprising: an elongate body having an embedded conductor extending along its length, and, a plurality of conductive connectors extending from the body for connection to an aircraft voltage reference to dissipate excess unwanted charge from a component of the harness.
- “harness” we mean a structure capable of retaining a conductor in a fixed location relative thereto.
- the body is substantially inflexible, therefore fewer mounting points are required.
- the harness may be a structural load bearing component of an aircraft, for example a wing spar or stringer.
- the embedded conductor is electromagnetically shielded, for example by a conducting sheath constructed from a metal foil.
- the conducting sheath may therefore be in electrical contact with the plurality of conductive connectors.
- the plurality of conductive connectors may be used for conducting static charge from the body to the fuel tank wall.
- the harness may have a first group of conductive connectors for wire shield binding, and a second group for static bonding.
- the second group are positioned intermittently along the length of the body, whilst the first group are at the ends of each body section.
- the plurality of conductive connectors may be clips configured to at least partially surround the body.
- the clips may be constructed from a carbon doped composite, and are therefore conductive.
- the clips are configured to hold the harness away from an aircraft fuel tank interior wall.
- the connectors may define a snap fit formation to receive the body.
- the body is at least partially constructed from a laminar composite, and the embedded conductor is embedded within the matrix material of the composite and positioned between adjacent layers of the laminate.
- the embedded conductor may be a wire or a printed circuit board.
- the body is at least partially constructed from a laminar composite and the printed circuit board comprises a planer substrate oriented substantially parallel with the composite laminate.
- the harness may define one (or more) raceway channel configured to receive a cable.
- the invention also provides an aircraft wing comprising a structural load bearing component having a substantially inflexible, elongate, composite body, which body has an embedded conductor extending along its length.
- the invention also provides an aircraft fuel tank comprising:
- the body is constructed from a glass-reinforced polymer.
- FIG. 1 is a cross-section view of an aircraft wing
- FIG. 2 is a perspective view of a harness in accordance with the present invention.
- FIG. 3 is a cross-section view of the harness of FIG. 2 taken at III-III;
- FIG. 4 is a cross-section view of the harness of FIG. 2 taken along IV-IV;
- FIG. 5 is a close-up view of the cross-section of FIG. 3 ;
- FIG. 6 is a cross-section view of an alternative harness in accordance with the present invention.
- FIG. 7 is a cross-section view of an further alternative harness in accordance with the present invention.
- FIG. 8 is a close up of a part of an aircraft wing.
- FIG. 1 a side cross-section of an aircraft wing 10 is shown having an upper skin 12 and a lower skin 14 , a spar 16 and a harness 18 .
- the spar 16 provides structural reinforcement for the wing across its span.
- the harness 18 comprises a body 20 being substantially rectangular in cross-section and being constructed from a glass fibre reinforced polymer (GFRP) material.
- the body 20 defines four cable groups 22 embedded therein and running substantially along the length of the body 20 .
- each cable group 22 comprises a plurality of cables 23 in a bundle surrounded by a conductive foil sheath 24 .
- the foil sheath 24 surrounds the bundle of cables 23 and acts as an electro-magnetic shield.
- the sheaths 24 break out of the body 20 and are bonded to an earth terminal 26 which is connected to the aircraft's earth.
- each of the cables 23 are electro-magnetically protected from the effects of the neighbouring cable group and from any external electro-magnetic radiation.
- the an alternative harness 1018 is shown having a body 1020 constructed from a carbon fibre reinforced polymer (CFRP) material comprising a plastic matrix 1028 embedded in which are carbon fibre sheets 1030 spanning the width of the harness 1018 .
- CFRP carbon fibre reinforced polymer
- Each of the cable groups 1022 lies between two of the carbon fibre sheets 1030 and, as such, forms part of the layer of the composite material.
- an alternative harness 118 is shown having a CFRP composite body 120 comprising a matrix material 122 in which several carbon fibre layers 124 are embedded.
- a printed circuit board (PCB 126 ) is embedded within the body 120 and lies between two adjacent layers of carbon fibre material 124 .
- the PCB 126 defines several conductor paths which run along the length of the stringer 18 to provide substantially the same functionality as the cables 23 .
- the harness 18 may comprise several individual harness components or modules which are joined at their ends.
- Mechanical connectors may be provided to give mechanical stability between each of the sub-components and, in particular, electrical connectors would also be provided to maintain connections between the cable ends 22 .
- Connectors may also be provided at the ends to bond the wire shields (i.e. sheaths 24 ) to the aircraft voltage reference.
- a cable harness 218 which may be structural in nature (e.g. on the inside of an aircraft fuselage) is similar to the harnesses 18 , 1018 , 1189 with the exception that three upstanding walls 350 , 352 , 354 form a pair of cable raceway channels 356 , 358 . Cable bundles 360 , 362 are installed in the raceway channels 356 , 358 .
- a plurality of cable groups 322 are embedded within the harness 218 , and are electromagnetically shielded such that interference from the bundles 360 , 362 is minimized.
- the aircraft wing 10 is shown in detail.
- the upper skin 12 and the lower skin 14 each define the boundary of a fuel tank 400 containing fuel 402 .
- a connector in the form of a clipping arrangement 404 is provided at the roof of the tank and comprises a base 406 , a first resilient arm 408 and a second opposite resilient arm 410 extending therefrom into the tank 400 .
- the harness 18 is suspended from the upper skin 12 (or any other appropriate structure at the roof of the tank).
- the body 20 is constructed from the non-conductive GFRP to prevent any conduction between the conductors/sheaths and the exterior surface of the body 20 .
- the body 20 is clipped between the two clips 408 , 410 such that it is spaced apart from the skin 12 (in order to prevent any arcing should static occur).
- the clips 408 , 410 are constructed from a conductive material such as carbon doped GFRP or CFRP in order to conduct any static which builds up on the body 20 to the tank wall 12 (i.e. to earth).
- the location of the clips 408 , 410 is determined by the requirement to conduct static away from the body 20 . Therefore the clips 408 , 410 can be spaced further apart than required for a flexible harness.
- the structural clips 408 , 410 may be interspersed with simple conductive connectors passing between the body 20 and the skin 12 to specifically conduct static, without structurally supporting the body 20 . This saves weight.
- the harness 18 can be made significantly thicker on its top side so as to extend to the skin 12 thus providing the necessary protection from static. If the body 20 is constructed from a material which is less prone to arcing than the air/fuel vapour mixture within the tank (e.g. GFRP) then the cable groups 22 are positioned closer to the wing skin 12 .
- GFRP the air/fuel vapour mixture within the tank
- the harness may be structural—e.g. a stringer running in a spanwise direction which as well as acting as a harness provides some structural rigidity to the aircraft wing.
- Known structural components may be replaced by structural harnesses according to the present invention.
- the body may form part of the structure within the aircraft fuselage or any other part of the aircraft body. It is envisaged that the body 20 , 120 could take the shape and form of any given structural or non-structural component within the aircraft body thus conforming to the packaging requirements of the cable harness.
- the harness body may be constructed from any suitable material depending on the structural and conductive properties required. In the event that it is positioned in the fuel tank, a non conductive outer surface is desirable (e.g. the matrix of a CFRP or GFRP) which is intermittently bonded to the aircraft structure.
- a non conductive outer surface is desirable (e.g. the matrix of a CFRP or GFRP) which is intermittently bonded to the aircraft structure.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Installation Of Indoor Wiring (AREA)
Abstract
Description
- The present invention relates to an aircraft cable routing harness. More specifically, the present invention relates to a cable routing harness having a conductor embedded therein, wherein the harness is a substantially inflexible structural member and may be used in a fuel quantity installation of an aircraft.
- Traditionally, cables are routed throughout aircraft and in particularly through aircraft wings using cable raceways. These raceways are generally constructed from aluminium and comprise channel sections into which cables can be secured. Such cables are often braided to provide electro-magnetic protection. The raceway serves to guide and secure the cables and protect them from external mechanical damage. The cables are often secured in place in the raceway channels using clips.
- Fuel quantity installation (FQI) cable harnesses are routed through aircraft fuel tanks, in particular through the tanks in aircraft wings. These harnesses are clipped to the aircraft structure to hold them in place. Such harnesses are often braided or routed in a multi-layered conduit to provide electro-magnetic protection. Such structures also provide multiple layer protection to ensure that the wires are not exposed, even if the outer layers are damaged.
- A problem with known raceways is that they add significant weight to the aircraft. Furthermore, the cables are relatively free to move within the raceways which may affect their proximity (i.e. potentially causing problems with electro-magnetic interference) and may cause friction between adjacent cables. This is undesirable. Further, known harnesses are relatively flexible and therefore must be clipped quite frequently along their length. This adds weight to the aircraft and makes the assembly process lengthy and costly.
- A further technical challenge in this field is to manage interference from adjacent conductors, and to prevent build up of static charge which could otherwise cause arcing.
- It is an aim of the invention to overcome or at least mitigate one or more of the above problems.
- According to a first aspect of the invention there is provided an aircraft cable routing harness comprising: an elongate body having an embedded conductor extending along its length, and, a plurality of conductive connectors extending from the body for connection to an aircraft voltage reference to dissipate excess unwanted charge from a component of the harness.
- By “harness” we mean a structure capable of retaining a conductor in a fixed location relative thereto.
- By providing a harness having an embedded conductor, the use of complex clips and channel section raceways is thereby avoided. Furthermore, the fact that the conductors are embedded within the harness means that their proximity can be maintained.
- Preferably the body is substantially inflexible, therefore fewer mounting points are required. The harness may be a structural load bearing component of an aircraft, for example a wing spar or stringer.
- Preferably the embedded conductor is electromagnetically shielded, for example by a conducting sheath constructed from a metal foil. The conducting sheath may therefore be in electrical contact with the plurality of conductive connectors.
- Alternatively, or in addition, the plurality of conductive connectors may be used for conducting static charge from the body to the fuel tank wall. The harness may have a first group of conductive connectors for wire shield binding, and a second group for static bonding. Preferably the second group are positioned intermittently along the length of the body, whilst the first group are at the ends of each body section.
- The plurality of conductive connectors may be clips configured to at least partially surround the body. The clips may be constructed from a carbon doped composite, and are therefore conductive.
- Preferably the clips are configured to hold the harness away from an aircraft fuel tank interior wall. The connectors may define a snap fit formation to receive the body.
- Preferably the body is at least partially constructed from a laminar composite, and the embedded conductor is embedded within the matrix material of the composite and positioned between adjacent layers of the laminate. The embedded conductor may be a wire or a printed circuit board.
- Preferably the body is at least partially constructed from a laminar composite and the printed circuit board comprises a planer substrate oriented substantially parallel with the composite laminate.
- The harness may define one (or more) raceway channel configured to receive a cable.
- The invention also provides an aircraft wing comprising a structural load bearing component having a substantially inflexible, elongate, composite body, which body has an embedded conductor extending along its length.
- The invention also provides an aircraft fuel tank comprising:
-
- a tank wall,
- a fuel quantity installation cable routing harness having an elongate body having a conductor embedded therein and extending along its length,
- wherein the elongate body is positioned in direct contact with the tank wall.
- Preferably the body is constructed from a glass-reinforced polymer.
- An example aircraft cable routing harness in accordance with the invention will now be described with reference to the accompanying figures in which:
-
FIG. 1 is a cross-section view of an aircraft wing; -
FIG. 2 is a perspective view of a harness in accordance with the present invention; -
FIG. 3 is a cross-section view of the harness ofFIG. 2 taken at III-III; -
FIG. 4 is a cross-section view of the harness ofFIG. 2 taken along IV-IV; -
FIG. 5 is a close-up view of the cross-section ofFIG. 3 ; -
FIG. 6 is a cross-section view of an alternative harness in accordance with the present invention; -
FIG. 7 is a cross-section view of an further alternative harness in accordance with the present invention; and, -
FIG. 8 is a close up of a part of an aircraft wing. - Referring to
FIG. 1 , a side cross-section of anaircraft wing 10 is shown having anupper skin 12 and alower skin 14, aspar 16 and aharness 18. Thespar 16 provides structural reinforcement for the wing across its span. - Referring to
FIG. 2 , theharness 18 is shown in detail. Theharness 18 comprises abody 20 being substantially rectangular in cross-section and being constructed from a glass fibre reinforced polymer (GFRP) material. Thebody 20 defines fourcable groups 22 embedded therein and running substantially along the length of thebody 20. - Referring to
FIG. 3 , eachcable group 22 comprises a plurality ofcables 23 in a bundle surrounded by aconductive foil sheath 24. Thefoil sheath 24 surrounds the bundle ofcables 23 and acts as an electro-magnetic shield. Referring toFIG. 4 , at positions along the length of the harness 18 (preferably at the ends of the harness) thesheaths 24 break out of thebody 20 and are bonded to anearth terminal 26 which is connected to the aircraft's earth. As such, each of thecables 23 are electro-magnetically protected from the effects of the neighbouring cable group and from any external electro-magnetic radiation. - Turning to
FIG. 5 , the analternative harness 1018 is shown having a body 1020 constructed from a carbon fibre reinforced polymer (CFRP) material comprising aplastic matrix 1028 embedded in which arecarbon fibre sheets 1030 spanning the width of theharness 1018. Each of thecable groups 1022 lies between two of thecarbon fibre sheets 1030 and, as such, forms part of the layer of the composite material. - Turning to
FIG. 6 , analternative harness 118 is shown having a CFRPcomposite body 120 comprising amatrix material 122 in which several carbon fibre layers 124 are embedded. A printed circuit board (PCB 126) is embedded within thebody 120 and lies between two adjacent layers ofcarbon fibre material 124. - The
PCB 126 defines several conductor paths which run along the length of thestringer 18 to provide substantially the same functionality as thecables 23. - It is conceivable that the
harness 18 may comprise several individual harness components or modules which are joined at their ends. Mechanical connectors may be provided to give mechanical stability between each of the sub-components and, in particular, electrical connectors would also be provided to maintain connections between the cable ends 22. Connectors may also be provided at the ends to bond the wire shields (i.e. sheaths 24) to the aircraft voltage reference. - Referring to
FIG. 7 , acable harness 218 which may be structural in nature (e.g. on the inside of an aircraft fuselage) is similar to theharnesses upstanding walls cable raceway channels raceway channels - A plurality of
cable groups 322 are embedded within theharness 218, and are electromagnetically shielded such that interference from thebundles - Referring to
FIG. 8 , theaircraft wing 10 is shown in detail. Theupper skin 12 and thelower skin 14 each define the boundary of afuel tank 400 containingfuel 402. A connector in the form of aclipping arrangement 404 is provided at the roof of the tank and comprises abase 406, a firstresilient arm 408 and a second oppositeresilient arm 410 extending therefrom into thetank 400. Theharness 18 is suspended from the upper skin 12 (or any other appropriate structure at the roof of the tank). - It will be noted that the
body 20 is constructed from the non-conductive GFRP to prevent any conduction between the conductors/sheaths and the exterior surface of thebody 20. - Being non-conductive, it is important to avoid the build-up of static charge on the surface of the
body 20. - As such, the
body 20 is clipped between the twoclips clips body 20 to the tank wall 12 (i.e. to earth). - Because the
body 20 is stiff (being constructed form GFRP) the location of theclips body 20. Therefore theclips - It is envisaged that the
structural clips body 20 and theskin 12 to specifically conduct static, without structurally supporting thebody 20. This saves weight. - It will be noted that instead of providing an air gap, the
harness 18 can be made significantly thicker on its top side so as to extend to theskin 12 thus providing the necessary protection from static. If thebody 20 is constructed from a material which is less prone to arcing than the air/fuel vapour mixture within the tank (e.g. GFRP) then thecable groups 22 are positioned closer to thewing skin 12. - Variations fall within the scope of the present invention.
- The harness may be structural—e.g. a stringer running in a spanwise direction which as well as acting as a harness provides some structural rigidity to the aircraft wing. Known structural components may be replaced by structural harnesses according to the present invention.
- Alternatively, the body may form part of the structure within the aircraft fuselage or any other part of the aircraft body. It is envisaged that the
body - The harness body may be constructed from any suitable material depending on the structural and conductive properties required. In the event that it is positioned in the fuel tank, a non conductive outer surface is desirable (e.g. the matrix of a CFRP or GFRP) which is intermittently bonded to the aircraft structure.
Claims (22)
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GBGB1018250.9A GB201018250D0 (en) | 2010-10-29 | 2010-10-29 | Aircraft fuel quantity installation routing harness |
GB1018250.9 | 2010-10-29 | ||
GBGB1018248.3A GB201018248D0 (en) | 2010-10-29 | 2010-10-29 | Aircraft cable routing harness |
GB1018248.3 | 2010-10-29 |
Publications (2)
Publication Number | Publication Date |
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US20120103685A1 true US20120103685A1 (en) | 2012-05-03 |
US9040821B2 US9040821B2 (en) | 2015-05-26 |
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Application Number | Title | Priority Date | Filing Date |
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US13/284,135 Expired - Fee Related US9040821B2 (en) | 2010-10-29 | 2011-10-28 | Aircraft cable routing harness |
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US (1) | US9040821B2 (en) |
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US20130161093A1 (en) * | 2011-12-22 | 2013-06-27 | Rolls-Royce Plc | Electrical harness |
US20130189868A1 (en) * | 2011-12-22 | 2013-07-25 | Rolls-Royce Plc | Electrical connectors |
US20140208770A1 (en) * | 2013-01-29 | 2014-07-31 | Rolls-Royce Plc | Component having insert for receiving threaded fasteners |
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